Thermally Induced Attitude Disturbance Control for Spacecraft with a Flexible Boom

摘要

A spacecraft with a flexible appendage is analyzed by a coupled system composed of a flexible boom and a rigid main body, which is described by the FEM. The thermally induced dynamic response of the boom shows a quasi-static displacement and superimposed vibrations, and consequently, the attitude angle disturbances have a pointing error (steady-state error) as well as vibrations. To attenuate both the vibrations and constant attitude disturbances, an active con- trol system combines the integral control with the original PPF, by using an embedded piezoceramic device as actuators and sensors.